US20160369697A1 - Cooled cooling air system for a turbofan engine - Google Patents

Cooled cooling air system for a turbofan engine Download PDF

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Publication number
US20160369697A1
US20160369697A1 US14/740,368 US201514740368A US2016369697A1 US 20160369697 A1 US20160369697 A1 US 20160369697A1 US 201514740368 A US201514740368 A US 201514740368A US 2016369697 A1 US2016369697 A1 US 2016369697A1
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Prior art keywords
air
engine
heat exchanger
gas turbine
cooling air
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Abandoned
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US14/740,368
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English (en)
Inventor
Frederick M. Schwarz
Paul W. Duesler
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RTX Corp
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United Technologies Corp
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Application filed by United Technologies Corp filed Critical United Technologies Corp
Priority to US14/740,368 priority Critical patent/US20160369697A1/en
Assigned to UNITED TECHNOLOGIES CORPORATION reassignment UNITED TECHNOLOGIES CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: DUESLER, PAUL W., SCHWARZ, FREDERICK M.
Priority to EP16174862.9A priority patent/EP3106646B1/fr
Publication of US20160369697A1 publication Critical patent/US20160369697A1/en
Assigned to RAYTHEON TECHNOLOGIES CORPORATION reassignment RAYTHEON TECHNOLOGIES CORPORATION CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: UNITED TECHNOLOGIES CORPORATION
Assigned to RAYTHEON TECHNOLOGIES CORPORATION reassignment RAYTHEON TECHNOLOGIES CORPORATION CORRECTIVE ASSIGNMENT TO CORRECT THE AND REMOVE PATENT APPLICATION NUMBER 11886281 AND ADD PATENT APPLICATION NUMBER 14846874. TO CORRECT THE RECEIVING PARTY ADDRESS PREVIOUSLY RECORDED AT REEL: 054062 FRAME: 0001. ASSIGNOR(S) HEREBY CONFIRMS THE CHANGE OF ADDRESS. Assignors: UNITED TECHNOLOGIES CORPORATION
Abandoned legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • F02C7/185—Cooling means for reducing the temperature of the cooling air or gas
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01P—COOLING OF MACHINES OR ENGINES IN GENERAL; COOLING OF INTERNAL-COMBUSTION ENGINES
    • F01P11/00—Component parts, details, or accessories not provided for in, or of interest apart from, groups F01P1/00 - F01P9/00
    • F01P11/12—Filtering, cooling, or silencing cooling-air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01P—COOLING OF MACHINES OR ENGINES IN GENERAL; COOLING OF INTERNAL-COMBUSTION ENGINES
    • F01P7/00—Controlling of coolant flow
    • F01P7/02—Controlling of coolant flow the coolant being cooling-air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
    • F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/08—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
    • F02K3/105—Heating the by-pass flow
    • F02K3/115—Heating the by-pass flow by means of indirect heat exchange
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/213—Heat transfer, e.g. cooling by the provision of a heat exchanger within the cooling circuit
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/231—Preventing heat transfer
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/303—Temperature
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present disclosure relates generally to turbofan engines, and more specifically to a cooled cooling air system for utilization within a turbofan engine.
  • Gas turbine engines such as those utilized on commercial aircraft, typically include a compressor section that draws in and compresses air, a combustor section where the compressed air is mixed with a fuel and ignited, and a turbine section across which the combustion gasses from the ignition are expanded. Expansion of the combustion gasses across the turbine section drives rotation of the turbine section, which in turn drives rotation of the compressor section.
  • Each of the compressor section, the combustor section, and the turbine section are contained within an engine core, and are connected by a primary flowpath that flows through each of the sections.
  • the fan Fore of the compressor section is a fan that drives air through a fan bypass duct surrounding the engine core.
  • the fan is connected to the turbine section via a drive shaft.
  • the fan is connected through a gear system, and the engine is referred to as a geared turbofan engine.
  • the fan is connected directly to a turbine in the turbine section via a drive shaft and the engine is referred to as a direct drive engine.
  • cooling air is provided from a cooling air system directly to the cooled components.
  • the cooling air in some examples is actively cooled.
  • a system for actively cooling the cooling air is referred to as a cooled cooling air system.
  • a gas turbine engine in one exemplary embodiment, includes an engine core defining a primary flowpath, and a nacelle radially surrounding the engine core.
  • the nacelle includes at least one bifurcation, and a cooled cooling air system including a heat exchanger.
  • the heat exchanger is disposed at least partially in the bifurcation.
  • the bifurcation is a lower bifurcation.
  • the heat exchanger is structurally mounted to the engine core via at least one bracket.
  • the heat exchanger is an air-air heat exchanger, and a cooling air stream originates in a fan bypass duct.
  • the cooling air stream exhausts into one of an aft portion of the fan bypass duct and an ambient atmosphere downstream of the fan bypass duct.
  • a spent cooling air exhaust nozzle is a thrust producing nozzle.
  • the heat exchanger is an orthoganol heat exchanger.
  • Another exemplary embodiment of any of the above described gas turbine engines further includes a fan fore of the engine core, and wherein the fan is connected to the engine core via a gearing system.
  • the cooled cooling air system includes a second heat exchanger, and wherein the second heat exchanger is at least partially disposed in the bifurcation.
  • the cooled cooling air system further includes a cooling air inlet door, the cooling air inlet door including a flow regulation feature.
  • the flow regulation feature is an articulating door controllably coupled to an engine controller such that the engine controller is operable to control a flow of air through the cooling air inlet.
  • the cooled cooling air system further includes a cooling air outlet door, the cooling air outlet door including a flow regulation feature.
  • the flow regulation feature is an articulating door, and the articulating door is controllably coupled to an engine controller such that the engine controller is operable to control a flow of air through the cooling air outlet.
  • An exemplary method for generating cooled cooling air in a gas turbine engine includes withdrawing fan bypass duct air from a fan bypass duct and withdrawing bleed air from a primary flowpath in an engine core, providing the fan bypass air and the bleed air to a heat exchanger in an engine bifurcation via ducting, transferring heat from the bleed air to the fan bypass air in the heat exchanger, and providing the cooled bleed air to at least one gas turbine engine component as cooled cooling air.
  • a further example of the above exemplary method includes withdrawing fan bypass duct air from a fan bypass duct including modifying a position of at least one articulating door at one of an inlet of the ducting and an outlet of the ducting.
  • a further example of any of the above exemplary methods further includes exhausting heated fan bypass duct air from the heat exchanger into one of an aft portion of the fan bypass duct and an ambient atmosphere downstream of the fan bypass duct.
  • exhausting the heated fan bypass duct air includes passing the heated fan bypass air through an exhaust nozzle, thereby generating thrust.
  • any of the above exemplary methods includes transferring heat from the bleed air to the fan bypass air in the heat exchanger comprises passing the bleed air through a plurality of pipes in the heat exchanger, and passing the fan bypass air across the pipes in the heat exchanger.
  • any of the above exemplary methods includes providing the fan bypass air and the bleed air to a heat exchanger in an engine bifurcation via ducting further comprises providing the fan bypass air and the bleed air to at least two heat exchangers in the engine bifurcation.
  • FIG. 1 schematically illustrates an exemplary gas turbine engine.
  • FIG. 2 schematically illustrates a front view of a gas turbine engine.
  • FIG. 3 schematically illustrates a cross section view of a fan nacelle at a bifurcation.
  • FIG. 4 schematically illustrates a cross sectional view of an alternate fan nacelle at a bifurcation.
  • FIG. 1 schematically illustrates a gas turbine engine 20 .
  • the gas turbine engine 20 is disclosed herein as a two-spool turbofan that generally incorporates a fan section 22 , a compressor section 24 , a combustor section 26 and a turbine section 28 .
  • Alternative engines might include an augmentor section (not shown) among other systems or features.
  • the fan section 22 drives air along a bypass flow path B in a bypass duct defined within a nacelle 15
  • the compressor section 24 drives air along a core flow path C for compression and communication into the combustor section 26 then expansion through the turbine section 28 .
  • the exemplary engine 20 generally includes a low speed spool 30 and a high speed spool 32 mounted for rotation about an engine central longitudinal axis A relative to an engine static structure 36 via several bearing systems 38 . It should be understood that various bearing systems 38 at various locations may alternatively or additionally be provided, and the location of bearing systems 38 may be varied as appropriate to the application.
  • the low speed spool 30 generally includes an inner shaft 40 that interconnects a fan 42 , a first (or low) pressure compressor 44 and a first (or low) pressure turbine 46 .
  • the inner shaft 40 is connected to the fan 42 through a speed change mechanism, which in exemplary gas turbine engine 20 is illustrated as a geared architecture 48 to drive the fan 42 at a lower speed than the low speed spool 30 .
  • the high speed spool 32 includes an outer shaft 50 that interconnects a second (or high) pressure compressor 52 and a second (or high) pressure turbine 54 .
  • a combustor 56 is arranged in exemplary gas turbine 20 between the high pressure compressor 52 and the high pressure turbine 54 .
  • a mid-turbine frame 57 of the engine static structure 36 is arranged generally between the high pressure turbine 54 and the low pressure turbine 46 .
  • the mid-turbine frame 57 further supports bearing systems 38 in the turbine section 28 .
  • the inner shaft 40 and the outer shaft 50 are concentric and rotate via bearing systems 38 about the engine central longitudinal axis A which is collinear with their longitudinal axes.
  • the core airflow is compressed by the low pressure compressor 44 then the high pressure compressor 52 , mixed and burned with fuel in the combustor 56 , then expanded over the high pressure turbine 54 and low pressure turbine 46 .
  • the mid-turbine frame 57 includes airfoils 59 which are in the core airflow path C.
  • the turbines 46 , 54 rotationally drive the respective low speed spool 30 and high speed spool 32 in response to the expansion.
  • gear system 48 may be located aft of combustor section 26 or even aft of turbine section 28
  • fan section 22 may be positioned forward or aft of the location of gear system 48 .
  • the engine 20 in one example is a high-bypass geared aircraft engine.
  • the engine 20 bypass ratio is greater than about six (6), with an example embodiment being greater than about ten (10)
  • the geared architecture 48 is an epicyclic gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3 and the low pressure turbine 46 has a pressure ratio that is greater than about five.
  • the engine 20 bypass ratio is greater than about ten (10:1)
  • the fan diameter is significantly larger than that of the low pressure compressor 44
  • the low pressure turbine 46 has a pressure ratio that is greater than about five (5:1).
  • Low pressure turbine 46 pressure ratio is pressure measured prior to inlet of low pressure turbine 46 as related to the pressure at the outlet of the low pressure turbine 46 prior to an exhaust nozzle.
  • the geared architecture 48 may be an epicycle gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3:1. It should be understood, however, that the above parameters are only exemplary of one embodiment of a geared architecture engine and that the present invention is applicable to other gas turbine engines including direct drive turbofans.
  • the fan section 22 of the engine 20 is designed for a particular flight condition—typically cruise at about 0.8 Mach and about 35,000 feet (1066.8 meters).
  • TSFC Thrust Specific Fuel Consumption
  • Low fan pressure ratio is the pressure ratio across the fan blade alone, without a Fan Exit Guide Vane (“FEGV”) system.
  • the low fan pressure ratio as disclosed herein according to one non-limiting embodiment is less than about 1.45.
  • Low corrected fan tip speed is the actual fan tip speed in ft/sec divided by an industry standard temperature correction of [(Tram ° R)/(518.7° R)] ⁇ 0.5.
  • the “Low corrected fan tip speed” as disclosed herein according to one non-limiting embodiment is less than about 1150 ft/second (350.5 m/s).
  • FIG. 2 schematically illustrates a front view of the gas turbine engine 20 .
  • the engine core 130 is contained within a fan nacelle 120 , and a fan bypass duct is defined between the fan nacelle 120 and the engine core 130 .
  • the fan nacelle 120 includes a pylon mount 110 for mounting the engine 20 to a wing of an aircraft.
  • the fan nacelle 120 includes a bifurcation 112 .
  • the bifurcation 112 is approximately 180 degrees offset from the pylon mount 110 and is referred to as a lower bifurcation.
  • Alternative engines can include additional bifurcations, or position the bifurcation at a different location.
  • some engines can include a bifurcation at position 114 .
  • the alternative engines can include the bifurcation in any other suitable position.
  • the cooled cooling air is provided to one or more components in the engine 20 and actively cools the component.
  • a cooled cooling air system 140 is included in the engine 20 .
  • the cooled cooling air system 140 uses one or more heat exchangers 142 to cool bleed air from the primary flowpath through the engine core 130 , and provides the cooled bleed air (referred to as cooled cooling air) to components in need of cooling within the gas turbine engine 20 .
  • the cooled cooling air is used to cool the engine components according to known cooling principles.
  • the cooled cooling air system 140 uses air drawn from the fan bypass duct as a heat sink for the cooled cooling air in the heat exchanger 142 .
  • the heat exchanger 142 in the illustrated example of FIG. 2 is disposed completely within the lower bifurcation 112 .
  • the heat exchanger can be partially disposed in a bifurcation 112 , 140 , with a remainder being housed within the fan nacelle 120 .
  • the heat exchanger 142 is structurally mounted to the engine core 130 via a mechanical bracket 170 , or other mechanical bracketing system.
  • FIG. 3 schematically illustrates a cross section of a bifurcation including a cooled cooling air system, such as the cooled cooling air system 140 of FIG. 2 .
  • the cross sectional view 200 illustrates a leading edge 202 of the fan nacelle 220 through to a trailing edge 204 of the fan nacelle 220 .
  • a heat exchanger 240 which is part of the cooled cooling air system 140 is included within the bifurcation.
  • Upstream of the heat exchanger 240 is an inlet 250 that allows an air stream 206 into the heat sink portion of the heat exchanger 240 .
  • the air stream 206 is a portion of the air that enters the bypass fan duct.
  • cooling air drawn from a bleed within the engine core passes through multiple pipes 242 within the heat exchanger 240 , and heat is transferred from the bleed air into the air stream 206 .
  • the heated air within the air stream 206 is referred to as spent air, and is exhausted from the heat exchanger 240 , and the cooled cooling air system, via a spent air outlet 260 .
  • the spent air outlet 260 is downstream of a fan duct nozzle into ambient atmosphere.
  • the spent air outlet can be upstream of the fan duct nozzle and is added back to the air in the fan duct prior to the fan duct air passing through the nozzle.
  • Each of the inlet 250 and the outlet 260 can include a flow regulation feature, such as articulating doors 252 , 262 .
  • the flow regulation feature is able to control the flow of air through the inlet 252 or outlet 260 , and therefore control the flow of heat sink air in the air stream 206 and through the heat exchanger 240 .
  • each of the articulating doors 252 , 262 is controllably coupled to an engine controller 270 , and the engine controller 270 controls the articulation of the doors 252 , 262 .
  • the articulating doors 252 , 262 can be controlled by actuators 254 , 264 that are in turn controlled by the engine controller 270 .
  • any other means of opening and closing the doors 252 , 262 can be utilized in place of the illustrated actuators 254 , 264 .
  • the outlet 260 can be shaped and constricted to function as a nozzle 280 and generate thrust, such an outlet is referred to as a thrust producing nozzle.
  • the thrust generated by the nozzle 280 reclaims a portion of the thrust lost when air is removed from the fan bypass duct to enter the air stream 206 .
  • the doors 252 , 262 can be included at only the inlet 250 or the outlet 260 .
  • FIG. 4 schematically illustrates cross sectional view 300 of an alternate fan nacelle at a bifurcation.
  • the fan nacelle of FIG. 4 is similar in construction to the fan nacelle of FIG. 3 , with a leading edge 302 , a trailing edge 304 , and a cooled cooling air system including a heat exchanger 340 positioned in the bifurcation.
  • the example of FIG. 4 includes multiple heat exchangers 340 , each of which includes multiple pipes 342 carrying bleed air.
  • Each of the heat exchangers 340 includes a corresponding inlet 350 that allows air from the fan bypass duct to enter the heat exchanger as the air stream 306 and operate as the heat sink for the bleed air passing through the pipes 342 . As the air stream 306 exits each of the heat exchangers 340 , the airstreams are merged into a single airstream that is then passed out of an outlet 360 .
  • each of the inlets 350 , and the outlet 360 include airflow regulation features, such as articulating doors 352 , 362 , that are capable of restricting or regulating the flow of air from the fan bypass duct into or out of the heat exchangers 340 .
  • the illustrated articulating doors 353 , 363 are controlled by an engine controller 370 .
  • each of the articulating doors at the inlets 350 can be controlled simultaneously as a single unit.
  • the controller 370 can control the articulating doors 352 independently of each other, allowing airflow through each of the heat exchangers 340 to be controlled independently of the airflow through the other heat exchangers 340 .
  • the articulating door 362 at the outlet can be arranged to form a nozzle 380 , and reclaim thrust in the same manner as the articulating door 262 illustrated in FIG. 2 , and described above.
  • the heat exchangers 240 , 340 are described and illustrated as orthogonal heat exchangers.
  • One of skill in the art, having the benefit of this disclosure will further understand that alternative air-air heat exchangers could be utilized in place of the illustrated and described orthogonal heat exchangers 240 , 340 , without significant modification to the above described features.
  • cooled cooling air systems can be included within a single engine, with a heat exchanger of each cooled cooling air system being included within one of the bifurcations 112 , 114 .

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US14/740,368 2015-06-16 2015-06-16 Cooled cooling air system for a turbofan engine Abandoned US20160369697A1 (en)

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Application Number Priority Date Filing Date Title
US14/740,368 US20160369697A1 (en) 2015-06-16 2015-06-16 Cooled cooling air system for a turbofan engine
EP16174862.9A EP3106646B1 (fr) 2015-06-16 2016-06-16 Moteur à double flux avec un système d'air de refroidissement et procédé correspondant

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US14/740,368 US20160369697A1 (en) 2015-06-16 2015-06-16 Cooled cooling air system for a turbofan engine

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US20180017342A1 (en) * 2016-07-14 2018-01-18 General Electric Company Entrainment heat exchanger
US20180038243A1 (en) * 2016-08-05 2018-02-08 General Electric Company Oil cooling systems for a gas turbine engine
US10100739B2 (en) 2015-05-18 2018-10-16 United Technologies Corporation Cooled cooling air system for a gas turbine engine
US10221862B2 (en) 2015-04-24 2019-03-05 United Technologies Corporation Intercooled cooling air tapped from plural locations
US10371055B2 (en) 2015-02-12 2019-08-06 United Technologies Corporation Intercooled cooling air using cooling compressor as starter
US10443508B2 (en) 2015-12-14 2019-10-15 United Technologies Corporation Intercooled cooling air with auxiliary compressor control
US10480419B2 (en) 2015-04-24 2019-11-19 United Technologies Corporation Intercooled cooling air with plural heat exchangers
US10550768B2 (en) 2016-11-08 2020-02-04 United Technologies Corporation Intercooled cooled cooling integrated air cycle machine
US10577964B2 (en) 2017-03-31 2020-03-03 United Technologies Corporation Cooled cooling air for blade air seal through outer chamber
EP3643884A1 (fr) 2018-10-22 2020-04-29 Rolls-Royce plc Moteur de turbine à gaz
US10669940B2 (en) 2016-09-19 2020-06-02 Raytheon Technologies Corporation Gas turbine engine with intercooled cooling air and turbine drive
US10677166B2 (en) 2015-08-12 2020-06-09 Rolls-Royce North American Technologies Inc. Heat exchanger for a gas turbine engine propulsion system
US10711640B2 (en) 2017-04-11 2020-07-14 Raytheon Technologies Corporation Cooled cooling air to blade outer air seal passing through a static vane
US10718233B2 (en) 2018-06-19 2020-07-21 Raytheon Technologies Corporation Intercooled cooling air with low temperature bearing compartment air
US10731560B2 (en) 2015-02-12 2020-08-04 Raytheon Technologies Corporation Intercooled cooling air
US10738703B2 (en) 2018-03-22 2020-08-11 Raytheon Technologies Corporation Intercooled cooling air with combined features
CN111727302A (zh) * 2018-02-23 2020-09-29 赛峰飞机发动机公司 包括次级路径中的热交换器的涡轮发动机
US10794288B2 (en) 2015-07-07 2020-10-06 Raytheon Technologies Corporation Cooled cooling air system for a turbofan engine
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